Anemometric regulator for aeroplanes.



R; ARNOUX.

ANEMOMETRIC REGULATOR roa- AEROFLANES. APPLECATFOIQ FILED JULY 2. 1913.

1,217,679, Patented Fe'b.27,1917

BEST AVAILABLE C UNITED STATES rarnn'r omen 1min umoux, or rams, rnmcn ToaZZ whom/it may concern: i

Be it known that I, Rmvli. Amvonx, a. citizen of the Republic of France, residing at Paris,'France, have invented certain. new and'useful Improvements in .AIIQIIIOIIIQUIC Regulators for Aeroplanes, ofwhich the follatter,

the-result that the power lowing is a specification. I

The object of this invention has been to devise effective means for increasing the stability of aeroplanes in flight. -With the foregoing obje'ctin view it IS contemplated by'the invention to employ an anemometric regulator so sensitive to the relative traveling speed of the aeroplane inthe atmosphere, and theattacking angle of the supporting planes of the machine as to .be simultaneously operable with respect to the means being provided intermediate said' regu plane controlling the admission of the explosive gases into the engine cylinders with of the motor is modified. Specifically speaking it is contemplated to utilize the anemometric means aforesaid to vary the propulsive force of the motor in an inverse direction to the sustaining force of the planes,

The drawing represents a diagrammatic view of aeroplane instrumentalities includ rznswmo) in which K and S are two constant factors characteristic-of the shape and dimensions of its supporting planes, V! the relative velocity of the air displacement with respect to the surrounding atmosphere, and finally f(t') a function of theirangle of attack or incidence, a shown to be always increasing and decreasing with this incidence a, at least for all the values of the latter practically employed.

When it is noted that, the lifting pressure acting on any aeroplane is a direct result of the propulsive powerof its motor screw, and that the action of the eddy currents of the wind strikinglconstantl against the supporting plan ll as t e ascending an descen g:

rents of the-atmo .varying not only lator and the engine of the aerothe ends 0 and o o'aof this surface or p ane function which experience has annuoun'rmc nncona'ron. r03 AEBOPLANEB.

' s mcaaan of mm. rum. t t d a 27, 1917,- Application am July a, ma. Serial Ill'o. 777 ,05li.'

here alwa 5 results in. t e *an'le o incidence i, but alsothe velocity V o the relative wind actingon said planes, it will be in'nnediatiel evident how im'portantit is to act, directy n the propelling wer of the motor screw of the aeroplane y an anemometric regulator'owing to the fact that since the said regulator is simultaneously sensible to the variations of the two factors V and i of its supporting crease of one-or both of them will beimmediately compensated for by a decrease 'or increase in the propelling power. r

The regulation of this power is effected by the anemometric regulator forming the subject matter of the present invention, in'the following manner:

- b is a small surface similar to the ing planes of the supportaeroplane and pivoted to of the two levers b and b of a parallelogram, so that this small surface remains constantly parallel to the supporting planes of the apparatus, whatever maybe their displacement under the action of the relative wind which strikes against it at every. moment; therefore, this surface is on the onehand constantly attacked at the same angle of incidence as that of the relative wind striking against the principal planes, and on .he other hand exposed to resistance to the travcling movement and th the sustaining force which are always proportional to the similar forces to which the planes themselves of the aeroplane are exposed. e

y In order that the supporting force, acting vertically upward in respect to' the path of the aeroplane on the anemometric' surface b, will be able to exert its regulating action on the'motive power, the ivoting points 0 and to. thdconnecting rods 1) and b are situated to -the rear of the upper fixed pivoting points'o and o" of the said connecting rods.

An antagonistic force, developed by the compression of a coil s rin'g e, -is opposed to the action of the re ative wind on the plane b. The spring c is arranged between the ends of two telescopic tubes 11 and d.

power, any increasebz de- Under these conditions,

The tube 01 is connected by a ivoting joint 0 to an operating lever a cape le of turning on a lpivot f, which leverithepilot of the ane. can stop in any-jde'si'red position meansofga suitable p c ing 'd v U e seigqqn itienslhe around itself, however,

' In the- ,taining force. of

lever 0 permits the aviator to directly control the power of the engine and to stop the whole anemometric system in the different positions corresponding to the ascending of the aeroplane, its horizontal forward movement, or its descending movement, without in any one of these different positions the anemometric device ceasing to exert its r lating action.

-ompanying drawing the arrow the direction along which the that is to say the aeroplane, is

D indicates plane I), moved.

The anemoinetric regulator is connected either directly, as indicated in the drawing, or indirectly to the valve 11 of the carbureter '1] regulating the quantity of explosive gases drawn in by the engine, in such a way that any increase or decrease of the relative wind constantly striking against the anemometric plane Ii corresponds relatively to a decrease of the increase of the power of the engine and.consequently of the propelling power of the screw operated thereby.

he axis a is fii'red relatively to the points 0 and 0 which are displaced with the plane It is noted that the axis 0 can turn in order to insure the displacement of the valve v. Relative to the joint connection 0 it should be borne in mind that the same is adapted to slide upon the rod'b; otherwise no functioning of the device would take place. The showing on the drawing is entirely diagrainmatic, however. Having thus described the invention, what is claimed is:

1. In a device for maintaining the sustaini force of aeroplanes substantially constant,

of. the variations of the sustaining force acting "thereon, a motor for propelling the aeroplane, and means intermediate said anemometric means and the motor for vary ing the propulsive force of said motor in .an inverse ratio to the sustaining force.

In a device for maintaining the susaeroplanes substantially constant. the combination of anemoinetric means adapted to be displaced by the effect of the variations of the sustaining force actingthereon, a motor for propelling the aeroplane, and means intermediate the. motor and the aneinoinetrie means for modifying the power of the motor as an incident to the effect of the variations of the sustaining force acting upon the ancinoinetric means.

In a device for maintaining the sustaining force of aeroplanes substantially constant, the combination of aneinometric means adapted to be dis ilaced by the effect of the variations of the s stainingforce acting thereon, a motor for propelling the aeroplane, valve means controlling the ad- EST AVAILABLE COP mission of an explosive mediutn to tlfi motor, and means intermediate the u'iemometric means and said valve means for acting on the latter to effect a variation in the war of the motor in correspondence with t e effect of variations of the sustaining force acting upon said anemometric means. 4. In a device for maintaining the sustaining force of aeroplanes substantially constant, the combination of anemometric means adapted to be displaced variations of the sustaining force acting a motor for propelling the aeroplane, valve means controlling the admission of an explosive medium to the motor, means intermediate the anemometric means and said valve means for acting on the lat ter to' effect a variation force of the motor in an inverse ratio to the variation in the sustaining force of the anemoinetrie means, and a lever common to said 'alve means and to the anemometric means. 5. In an air craft, propelling means for the air craft, an adjustable power controller therefor whereby the power supplied through said propelling means may be varied, and a pressure responsive device connected to ad ust said ower controlling means to vary ing power in re sponse to variations in wind pressure.

6. In a device for maintaining the sustaining constant, means adapted to be displaced by the effect of the variations of the thereon,

verse ratio 'to-the air pressure.

I. In a device for maintaining the sustaining force of constant. the combination of anemoinctric means adapted to "beidisplaced by the effect of the variations of the air thereon, a motor for prope plane, y and the anemometric means the power of the motor asan effectof the variations of the air pressure actin upon the anemometric means.

8. n a device for maintaining the sustaining force of' aeroplanes substantially constant, the combination of anemometric means adapted to bedisplaced by the effect of the variations of the air pressure acting thereon, a motor for propelling the aeroplane, valve means controlling the admission of an explosive medium to the motor, and means intermediate the anemoinetric means and said valve means foracting on the latter to effect a variation in the power of the motor in correspondence with the effect of variations of the air pressure acting upon said anemoinetric means.

pressure acting ling the aero- 1e and said valve means force of the propelling means at 35 by the air pressure acting emma 9. In a device for taining force of constant, the combination of anemometric means adapted to be displaced by the effect of, the variations of the air pressure acting thereon, a motor for propelling the aeroplane, valve means controlling the admission of an'explosi've medium to the motor, means intermediate the anemometric means for acting on the latter to effect a variation in the propulsive force of the motor in aninverse ratio to the variation in the air pressure of the anemaintaining the susmometric means, and a lever common to said valve means and to the auemometric means.

10. In an aeroplane, means for maintaining the sustaining force of the aeroplane substantially constant comprising propelling means for the aeroplane, anemometric means, and means eonnectingthe.propelling means and the anemometr c means an operative-to vary the propulsive force of the propelling means in inverse ratio to the a r pressure acting on the anemometric means.

11. In an aeroplane having a sustaining surface and propelling means, metric plane hav ng means for inta'ming g'it in substantial parallelism with the sustaining v surface at movable relatively thereto under the pressure of wind acting thereon, and means operative by said anemometric plane for controlling the propulsive letermined on said anemometric plane.

12. In an aeroplane having a sustainir'ig surface and propelling means, an anemometric surface Having means for maintain- 40 log it constantlyfin parallelism with the sustaining surface, said 'anemometric surface being subject to the influence of air pres sure tending to move it in one direction and also subject to the influence of counterbalaeroplanes substantially an anemoancing means tending to move it in an opposiw direction, and means operative by said anemometric surface for varying the propulsive force of the propelling means as etermined by the air pressure acting on said anemometric surface.

13. In an aeroplane having a sustaining surface and propelling means, an anemo metric surface movable in one direction under the influence of air pressure acting thereon and having means acting to balance the effect of the air n'essure on said anemometric surface, and means controlled by the anem'ometric surface for varying the propulsive force of the propelling means in inverse ratio to the air pressure acting on said aneinometric. surface.

14. In an aeroplane having a surface and propelling means, anemometric means movable under the influence of air pressure acting thereon and counteracting the influence of such uir pres sure thereon, means controlled by said ane mometric means for varying the propulsive force of the propelling means as determined by the air pressure acting on said anemometric means, and means for modifying the force of said counteracting means.

15. In an aeroplane having a sustaining surface and propelling means, anemoinetrie means movable under the influence of air pressure, a spring opposing such movez-nent of the anemometric means, means controlled by said anemometric means for varyingthe propulsive force of the prc elling means in inverse ratio to the air presv e acting there on, and manual control means ing the force of said spring.

In testimony whereof I affix my signature in presence of two witnesses.

RENE ARNOUX.

sustaining having means for modify 

